Engine controller



Dec. 20, 1949 J. DOLZA ETAL ,4

ENGINE CONTROLLER Filed Feb. 5, 1944 12 Sheets-Sheet 1 illllligl HIHIHHHI A4 MHZZ Dec. 20, 1949 Filed Feb. 3, 1944 J. DOLZA ET AL- ENGINE CONTROLLER 12 Sheets-Sheet 2 Dec. 20, 1949 J. DOLZA ET AL ENGINE CONTROLLER l2 Sheets-Sheet 3 Filed Feb. 5, 1944 Dec. 20, 1949 J. DOLZA ET AL ENGINE CONTROLLER l2 Sheets-Shem 4 Filed Feb. 3, 1944 Dec. 2% 1949 Ma. DOLZA EI'AL ENGINE CONTROLLER Film Feb. 3, 1944 Dec. 20, 1949 J. DOLZA ETAL ENGINE CONTROLLER l2 Sheets-Sheet 6 Filed Feb. 3, 1944 Dec. 20, mm J. DOLZA ETAL EAQIASZ ENGINE CONTROLLER Filed Feb. 3, 194A l2 Sheets-Sheet 7 Dec. 20, 1949 Filed Feb. 3, 1944 J DOLZA ET AL ENGINE CONTROLLER 12 Sheets-Sheet 8 Pas/770M; 0F PIN 214 mu-11m M ""7 a :g a

l2 Sheets-Sheet 9 J. DOLZA ET AL ENGINE CONTROLLER Filed Feb. 29, 1944 M mw ua Dec. 20, 1949 J. DOLZA ETAL ENGINE CONTROLLER l2 Sheets-Sheet 10 Filed Feb. 5. 1944 um R kmwk MSK R 3 wmawnwml NO/J/Ffid 40035 H Faun/3i woe; JNVJ N d1] N11 no? %N .wu

Dec. 20, 1949 J. DOLZA El AL ENGINE CONTROLLER Sheets-Sheet ll Filed Feb. 3, 1944 QAQLASZ Dec. 20, 1949 J. DOLZA ETA! ENGINE CONTROLLER l2 Shee'l;sSheet 12 Filed Feb. 3, 1944 Patented Dec. 20, 1949 ENGINE CONTROLLER John Dolza, Arthur W. Gaubatz, Peter W. Perish,

and Frank W. Kerfoot, Indianapolis, Ind., assignors to General Motors Corporation, Detroit, Mich., a corporation of Delaware Application February 3, 1944, Serial No. 520,878

39 Claims. (Cl. 123103) This invention relates to the control of the fuel intake pressure of an airplane internal combustion engine which is supercharged by a main supercharger driven by the engine at a fixed speed ratio and by an auxiliary supercharger driven by the engine through a variable speed drive.

It is the object of the present invention to control the variable speed drive connecting the engine with the auxiliary supercharger so as to obtain auxiliary supercharger speed as a function of selected manifold pressure and altitude air inlet scoop pressure or carburetor inpact pres sure and, at the same time, stay below borderline detonation of the engine for whatever type of fuel or fuels be used. In the disclosed embodiment of the invention, this object is accomplished by providing an infinitely variable fiuid coupling between the engine and auxiliary supercharger the action of which coupling is controlled by vary ing the quantity of hydraulic fluid therein and this is accomplished by shifting a coupling scoop or tube which determines the rotating level of fluid in the coupling. The nearer the coupling scoop is to the axis of rotation of the coupling, the less will be the coupling slip and the greater the coupling drive ratio. The coupling scoop is shifted automatically by a controller which is responsive to variation in impact pressure and to variation in pressure selection. Impact pressure is a pressure function of static (altitude) atmospheric pressure plus dynamic impact pressure caused by the air speed of the airplane minus the restrictions encountered by the air flowing within scoop to the engine. Impact pressure varies with altitude and airplane speed. The control of the operation of the fluid-coupling controller in response to variation in pressure selection is obtained by coordinating the fluid-coupling controller with a boost controller or throttle valve regulator by which the throttle valve is automatically moved so as to maintain a certain fuel intake pressure which is selected by manual operation. The coordination between the regulator and coupling controller is such that, in response to increase in pressure selection, the ground level startin position of the coupling scoop moves near to the couplin axis, so that the ground level starting ratio of the drive between the engine and auxiliary supercharger increases as pressure selection increases beyond a certainlow value. From that ground level starting position of the coupling scoop which has been determined by the pressure selection or datum adiustment of the throttle regulator, the coupling scoop moves toward the coupling axis as altitude increases. These devices provide that whatever pressure is selected will be maintained by the combined operation of the main and auxiliary superchargers as altitude increases. In order that a selected pressure suitable for normal military power can be maintained up to a certain high altitude, the fluid coupling ratio should increase with altitude up to its maximum (for example but at no time should it increase enough to cause manifold pressure in excess of borderline detonation. Emergency power and its corresponding manifold pressure represents power in excess of the military power. For this operating condition the drive ratio of coupling is usually greater for military power but does not exceed borderline detonation when borderline detonation altitude is reached. After the last mentioned altitude is reached (which is less than the altitude attained Without detonation when a normal military pressure is selected) the coupling ratio must increase at a lesser rate at altitude continues to increase so that the pressure actually obtained will not cause detonation. The present invention provides means for reducing the rate of increase of fluid-coupling ratio for further increase of altitude after an altitude is reached at which the selected pressure is almost at the detonation point. The result is that the pressure actually obtained with wide open throttle begins, above that altitude at which the selected pressure is close to the detona tion point, to fall off as altitude further increases so that the altitude which is critical for the normal military pressure selection can be attained Without detonation and without substantial reduction in engine power output. In other words, in an emergency, the engine is caused to operate with maximum emergency power up to an altitude such that detonation would occur; and, thereafter, the power is reduced only enough to avoid detonation.

A further feature of the invention resides in the provision of means for automatically increasing the intake pressure obtainable when an anti-det onant is being supplied to the engine and means controlled by fluid under pressure for preventing such increase in pressure when the supply of anti-detonant is exausted.

Further objects and advantages of the present invention will be apparent from the following description, reference being had to the accompanying drawings wherein a preferred embodiment of the present invention is clearlv shown.

oneness In the drawings:

Fig. i is a diagram of the fuel induction system with which this invention can be associated. The type of fuel system can be varied.

Fig 2 is a diagram of a circulatory system.

Fig. 3 is a fragmentary longitudinal sectional view of the auxiliary supercharger unit with hydraulic coupling shown diagrammatically in Fig. 2, the sectional view of the hydraulic coupling shown in Fig. 3 being on the line 33 of Fig. 4.

Fig. 4 is a fragmentary side view of the auxiliary supercharger unit, this view being taken in the direction of arrow 4 of Fig. 3.

Fig. 5 is a fragmentary sectional View on line r-5 of Fig. 4.

Fig. 6 is a fragmentary view of the auxiliary supercharger unit looking in the direction of arrow 3 of Fig. 4.

Figs. 7a and 7b taken together constitute a fragmentary view looking in the direction of arrow l of Fig. 6, that part which is shown in section being a sectional view on line 3-4! of Fig. 5.

Fig. 8 is a sectional view of the throttle valve regulator shown in Fig. 4 and is taken on section line 88 of Fig. 4.

Fig. 9 is a fragmentary sectional view on line 9-9 of Figs. 8 and 11.

Fig. 10 is a view similar to Fig. 8 and is a fragmentary sectional view of the fluid coupling controller and is taken on the line ifli0 of Fig. 6.

Fig. 11 is a fragmentary front view of the right end cover plate of the fluid coupling control and is taken in the direction of arrow B i of Fig. to.

Fig. 12 is a sectional view on the line i2-i2 of Fig. 11.

Fig. 13, Fig. 14, Fig. 15 are, respectively, sec-' tional views taken on line iS-it, t l-i i, and

i5-i5 of Fig. 8.

Figs. 16 and 1'7 are fragmentary sectional views taken, respectively, on the lines iii-i6 and ili l of Fig. 13.

Fig. 18 is a fragmentary side view of the throttie controller TC of Fig. 6 and is drawn to a larger scale than Fig. 6.

Fig. 19 is a View looking in the direction of the arrow 19 of Fig. 18.

Fig. 20 is a fragmentary side view of the fluid coupling controller FC of Fig. 7a, and is drawn to a larger scale than Fig. 7a.

Fig. 21 is in part a plan view of the mechanism shown in Fig. 20 and is in part a sectional view, the section being taken on the line 2i-2I of Fig. 20.

Fig. 22 is a mechanical diagram to show the operation of the fluid coupling controller without modification by the throttle regulator.

Fig. 23 is a fragment of the diagram of Fig. 22 drawn to a larger scale.

Fig. 24 is a diagram similar to Fig. 22 to show the operation of the fluid coupling controller when modified by the throttle regulator.

Fig. 25 is a fragment of the diagram shown in Fig. 24 and is drawn to a larger scale.

Fig. 26 is another diagram showing the operation of the fluid-coupling controller particularly with respect to the derivation of the shape of the control cam of the controller.

Fig. 27 is a fragment of the diagram shown in Fig. 26 drawn to a larger scale.

Figs. 28, 29 and 30 are charts indicating the operation of the fluid coupling controller.

Fig. 31 is a fragmentary longitudinal sectional view gt a modification of the regulator shown in ig.

Fig. 32 is a. sectional view on line 82-32 of Fig. 31.

Fig. 33 is a fragmentary side view looking in the direction of arrow 33 of Fig. 32.

Fig. 34, which is on the same sheet with Fig. 2'1, is a diagram showing the operation of the modifled regulator.

Fig. 35 is a diagrammatic view of an apparatus embodying applicants invention.

The fuel induction system with which this invention can be associated is shown diagrammatically in Fig. 1. The air enters the air scoop A and flows thru a carburetor B having a valve V for controlling the quantity of air which is later to be mixed with liquid fuel regulated by the carburetor. Carburetor B is connected by passage C with the inlet of auxiliary supercharger D having an impeller d1 mounted on a shaft d: driven by a gear (is meshing with a gear d4. The outlet casing d of supercharger D is connected by passage E with the inlet of the engine stage supercharger F, or main supercharger, having an impeller f1 driven directly by the engine driven shaft f2. The outlet casing f of supercharger F is connected with engine intake manifold G.

Liquid fuel is directed by nozzle J to the air flowing through passage E.

The auxiliary supercharger impeller d1 is driven by the engine thru an infinitely variable fluid coupling H having a driven vane member hr attached to a hollow shaft 712 connected with the gear d4. The driving vane member ha of the coupling H is attached to an engine driven shaft in. To the driving vane member ha there is attached an annular hood he which surrounds both vane members of the coupling. The motion transmitting fluid for the coupling passes thru the hollow shaft he and then radially between the coupling members. From member ha oil passes out through a number of holes he into the hood he so that the rotary level of oil in the hood is substantially the same as in the coupling.

In order to vary the slip percentage or coupling ratio the rotary oil level is varied by changing the position of a coupling scoop h'z shown in Fig. 2. The further the coupling scoop is from the axis :r-zl of the coupling, the lower will be the rotary oil level and the greater the slippage and the lesser the coupling ratio. As the coupling scoop h? is moved downwardly in Fig. 2, so as to bring its scooping end nearer to the axis :r-y, the

rotary oil level will be raised and likewise the coupling ratio. The oil which flows out the coupling scoop h is received by a vessel R having an outlet leading into a pipe S which leads to the inlet of a scavenger pump T which pumps both liquid and air and delivers the same to an oil cooler and/or tank K. An oil supply pump L withdraws oil from tank K and forces it thru a cleaner M, and thence to a pipe N which leads to the shaft bearings of the supercharger unit and to a pipe 0 which conducts oil to the respective servo-motors of the valve regulatorTC and the coupling control FC to be described. The oil in excess of bearing requirement is released by a relief valve P and flows into a recess Q provided by a bearing for the right end of shaft hz. This oil flows into the fluid coupling and is returned to the oil tank K by the scavenger pump T according to the position which the coupling scoop 'h-z occupies with respect to axis of the coupling.

. The coupling scoop hl shown in section Figs. 7a and 7b is adJusted automatically by the fluid coupling controller designated in its entirety by FC. The controller F is responsive to changes in altitude and is also under the control of the throttle valve regulator TC shown in Figs. 4 and 6 above the fluid coupling controller FC.

The instruments FC and TC are somewhat similar in construction. The throttle valve regulator controller TC will first be described with particular reference to Figs. 8 and 13 to 17.

The framework of the controller TC comprises a housing 2 and a bracket 4 secured by a bolt 6, and screws 6a. The housing 2 is provided with mounting feet 1 (Fig. 6) adapted to be secured to the auxiliary supercharger frame ASF. The pressure operated mechanism for controlling the position of the throttle valve V (Figs. 1 and 6) is located within the housing 2. As shown in Figs. 4 and 6 screws I0 secure to the housing 2 end plate or head 8 in which certain fluid passages are formed, for a purpose later set forth.

Referring to Fig. 6, the carburetor throttle valve V is rotated by an arm II connected by a link I2 with the stud I3 of a differential bell crank lever I4. The lever I4 is enlarged to form a hub which receives the outer race of a ball bearing I5, the inner race of which is supported by a stud I1 carried by an arm I8 which is secured to a shaft rotatably supported by the bracket 4. The lower end 28 of the lever I4 (Fig. 6) is pivotally connected at 29 with a link 30 pivotally connected at 3I with a piston rod 32 attached in any suitable maner to a piston 34 (Fig. 8) slidable in a cylinder 36 formed in the housing 2. The piston 34 is normally held in the position shown in Fig. 8 by a spring 38 located between the piston 34 and a cylinder head 40 which is fixed in one end of the cylinder 36 and which has a sleeve 42 formed at the center thereof' to provide a bearing in which one endof the piston rod 32 slides. Another cylinder head 44 is located in the opposite end of cylinder 36 and provides an annular extension 46 received in a hole 48 in bracket 4. The cylinder head 44 has a centrally disposed annual extension 52 in which is received a bushing 54 which provides a second bearing for the piston rod 32. A suitable seal 56 is supported within the extension of head 44 to prevent any leakage of fluid around the piston rod.

The piston 34 and cylinder 36 constitute a servo-motor for automatically operating the differential lever I4 to move the throttle valve V of the carburetor. Oil pressure, as controlled by an automatic valve, provides the motive power for moving the piston. To effect movement of the piston 34, oil under pressure is supplied by pipe 0, T-coupling O1 and pipe 02 to a passage 60 (Figs. 4, 6, 13, 14 and 15) provided by housing 2 from an oil pressure source represented in Fig. 2 as pump L. Passage 60 leads to passage 62 (Fig. 14) connected with an annular groove 63 (Fig. 8) in a tubular valve guide 64 connected with the interior thereof by a plurality of ports 65 located in an annular row. Guide 64 supports a valve 66 having lands 61 and 68 which control communication between ports 65 and either of the groups of valve guide ports 69 and 10, each group being a plurality of ports as shown in Fig. 14. One of the ports 69 is wider than land 61 as shown in Fig. 9 to provide for restricted circulation of oil through the controller even when land 61 is located as shown in Fig. 8. Ports 69 lead to valve guide groove 1I leading through passage 12 to the right side of piston 34. Ports 10 lead to valve guide groove 13 leading through passages 14, 15 and 16 (Fig. 16) to the left side (Fig. 8) of piston 34. A spring 11 located in a pocket 18 between housing 2 and bracket-4 urges the guide 64 against a shoulder 19 provided byhousingZ.

Valve 66 is connected by rod 80, clevis BI and pin 82 with a lever 83 pivoted on a :pin 84 carried by a bridge 85 connecting movable end plates 86 and 81 of metal bellows 88 and 89, respectively, having relatively fixed end plates 90 and 9|, respectively. Screws 93 secure the plate 9I to housing 2 with a sealing gasket 92 between them.

The interior of bellows 89 is connected either with the supercharger casing f or with the engine intake manifold G through apertured disc 94 (carried by plate 9|), pocket 95, cross passage 96, horizontal passage 98 (Fig. 15) and pipe 99 (Fig. 6). Bellows 88 is evacuated so that the bellows system is compensated for changes in atmospheric pressure and is responsive only to changes in engine intake pressure. Spring I00 in bellows 89 and springs ml and I02 in bellows 88 are so constructed and calibrated that the relation of the movements of the pin 84 to changes in engine intake pressure is substantially a fixed linear relation.

The location of valve 66 is determined partly by the pressure within bellows 89 and partly by a pressure selecting cam I 05 against which the upper end of lever 83 is urged by a spring I06 located in a recess I01 formed in housing 2 and closed at one end by a plug I08. Cam I05 is attached to a shaft IIO which is journalled in a bushing III secured to housing 2 (Fig. 13). Shaft H0 is gripped by the clamping hub. H6 (Fig. 18) of a lever II1, the hub being tightened by a clamping screw II8. Stud II9 fixed to lever II1 provides a pivotal connection with a link I20 which is retained upon the stud I I9 by a nut I2 I. Link I20 is connected to a stud I22 attached to lever arm I24 (Fig. 6) and is retained by a nut I23. Arm I24 is integral with arm I8 which through the shaft 20 is manually operated by a lever I25 known as the main control lever. The location of selector cam I05 by the main control lever I25 operating through the lever II1 selects working pressures from 25 to 65 inches of mercury, absolute, for example, which are indicated by a pointer I26 which moves past graduations I21 on a dial plate I28 carried by housing 2 (Fig. 18).

The device is calibrated for a certain specified pressure by holding lever 232 pivoted at 233 (Fig. 18) to a fixed height above pads 1 (Fig. 6), rotating lever II1 until roller 230 pivoted on lever 'I I1 contacts cam 23I in lever 232, applying the specified pressure to bellows 89, bending pointer I26 to indicate the specified pressure on dial I21, and adjusting the location of pin 84. An adjustment of the pin 84 is made until the piston 34 is in a balanced condition, that is, floating and not touching either end of the cylinder. In order to adjust the location of pin 84 the bellows plate 90 has a stem I30 (Fig. 8) received by a tubular boss I3I on the plate 8 and in which is provided a tapped hole I32 for receiving an adjustable stop screw driver I33 having a screw blade slot I 34 and locked by a nut I35. Screw I33 has a plain central bore receiving a screw I36 which retains a cover cup I31 and which threads into the stem I30 of plate 90 and which will draw the stern against the stop screw I33. To make the adjustment, remove the screw I36 and cover I31, loosen nut I35, apply oil pressure at passage 60. If piston 34 ,moves inwardly to left position in cylinder 36, turn screw I33 out until the piston 34 just begins to move right. This will indicate that the valve lands 61 and 66 have moved slightly to the left of the ports 69 and I0. Turn screw Ill slightly in the opposite direction until movement of piston ceases. This calibration should take place while the controller TC is being vibrated in order to cancel out frictional hysteresis. If, instead of moving inwardly when the oil pressure is applied in passage 60, the piston 34 stays in the outward position shown in Fig. 8, the screw I33 is turned inwardly until the piston starts moving to the left. Then the screw is turned slightly outwardly until movement of the piston ceases. After the adjustment is made, nut I36 is tightened and cover I31 and screw I36 are replaced and sealed.

During operation of the controller the bellows chamber I (Fig. 8) in housing 2 contains oil in order to dampen vibration of the bellows. Oil for this purpose is principally that which is dis charged from the servo cylinder 36. When valve 66 is moved to the right from the position shown in Fig. 8 to connect ports 65 and 69 in order that the piston 34 will move left, the oil on the left side of the piston will be discharged through passages 16, I5, I4 (Fig. 16) groove '13 (Fig. 8) and through the guide 64 to the chamber I10. When valve 66 moves left from the position shown to connect ports 65 and 10, oil at the right of the piston 34 is discharged through a passage 12, groove 1 I, guide 64, pocket I8, a passage III (connected with pocket I8 as shown in Fig. 9) and into chamber I10. Chamber I10 drains into a pocket I12 in plate 8 connected by a flow restricting hole I13 with a drain I14 (Fig. 4) with which a pipe I'I'5 may be connected. During operation of the controller, oil rises in the chamber I10 and overflows through passage I16 and passes down the drain I14 and pipe I into the housing 2' of fluid coupling controller FC.

Generally the leakage of oil past the land 61 and through the oversize port 69 (Fig. 9) when valve 66 is in the normal position shown, will provide for oil circulation at a rate sufficient to avoid congealing of the oil and allows oil, which would be otherwise trapped in the system, to circulate, to provide for immediate operation when the engine is cold. However, if the foregoing procedure should prove inadequate, a temperature controlled oil by-pass can be provided. As shown in Figs. 9, 13, 14, and 15, high pressure oil inlet passage 60 is connected with bellows chamber I10 through a by-pass including passages I90, I9l, I92 and Ill. As shown in Dolza Patent No. 2,451,204, this by-pass is controlled by a thermostat valve which maintains the by-pass open until the oil has become warm enough for proper operation of the throttle controller. If the thermostat valve is'not required. this by-pass is permanently closed by a plug I95.

Valve V is opened manually by counterclockwise movement of lever I25 which is connected with the pilots throttle lever in any suitable manner not shown. When lever I25 is so moved, servo piston rod 32 remaining fixed, the differential lever I4, 28 moves to the right and rotates clockwise to cause valve V to rotate counterclockwise from the idle position shown in Fig. 6. The manual control of valve V is suiiicient for takeoff from ground level or to make a safe landing in case of failure of oil-pressure in servo-cylinder 36 (Fig. 8), in which event spring 38 will return the piston 34 and rod 32 to normal position.

Lever I25 is positioned by the pilot for the purpose of selecting a pressure to be maintained by the automatic throttle controller TC. If, for

example, the required pressure is Kg, the pilot moves the throttle lever to such position on a quadrant that the movement which is imparted to lever I25 is sufficient to cause lever II! to be moved counterclockwise to a position such that pointer I26 is opposite the 60" mark on the dial I28. Cam I05 (Fig. 8) moves counterclockwise to permit spring IIII to move lever 63 counterclockwise and valve 66 to right to connect ports 65 and 69. Pressure fluid then flows into the right end of cylinder 36 and rod 32 moves left and valve V opens further than it was opened by manual operation of lever I25. The intake pressur increases and bellows 89 expands to cause pin 34 to move left and valve 66 to move toward the posi tion of equilibrium or balance in which ports 00 and I0 are covered. When the valve V has been opened sufliciently to cause the intake pressure to equal the selected pressure, valve 66 will be in position of equilibrium. As altitude increases the piston rod 32 moves left to increase the opening of valve V in order to maintain the selected pressure; and, as altitude decreases, the piston rod moves right to decrease the opening of valve V in order that the selected pressure will not be exceeded. The extent to which the valve V is opened by the combined effect of manual operation by the pilots throttle lever and of automatical operation by the throttle controller TC varies somewhat according to the pressure selected. Over a substantial range of high pressure selections, the valve V can be brought to such wideopen position that it offers no appreciable restriction to air flow.

The pressure in manifold G (Fig. 1) is dependent on the position of throttle valve V and the speed of the superchargers. The speed of main supercharger F is solely dependent on engine speed. The speed of auxiliary supercharger D is dependent on engine speed and the coupling ratio of fluid coupling H which is controlled in response to altitude and pressure selection by the fluid coupling controller FC which will now be described.

The fluid coupling controller F0 is similar in construction to the throttle controller TC. The parts of controller FC shown in Fig. 10 which are similar to parts of the throttle controller TC shown inFig. 0 are given the same reference numerals with a prime appended. Like controller TC, controller FC has a housing 2' closed at the left by a plate 8 and at the right by a plate 4a which is similar to the vertical plate 4a of bracket 4 of controller TC. Like controller TC,

controller FC has a servo-motor including a piston rod 32'. Rod 32' is connected by a pin 200, link 20I, and pin 202 with coupling scoop hq (Fig.

, 7a). The admission of pressure fluid to the cylinder 36' of the servo-motor is controlled by a valve 66 (Fig. 22) slidable in a guide 64'. Valve 66' is moved by lever 83' which is under the control of impact pressure and a cam 2I0. Bellows 88 is evacuated and bellows 89' (Fig. 10) is conconnected either with the air scoop A (Fig. 1) or with the impact chamber (not ,shown) of carburetor B. These bellows enclose springs (not shown) similar in function to the springs I00, IOI, I02 enclosed by the bellows 88 and 89 of controller TC; and the springs enclosed by bellows 88 and 09' are so constructed and calibrated that the pin 84 supporting lever 83' moves in a predetermined relation to changes in impact pressure.

Cam 2I0, against which lever 83' is urged by spring I01, is integral .with shaft 2I I eccentrically journalled in a shaft 2 I 2 Journalled in hous- 9 ing 2' (Fig. 21). Shaft III is operated by the servo-piston-rod 22' through means including a link 2l2 (Fig. 7a) connected by pin 2 with the head of pin 20!], and connected by pin 2i! with a lever 2|. attached to shaft 2| I and having an arm 2ll carrying an adjustable stop screw 2l8 locked in adjusted position by a nut 2". As the plane ascends impact pressure decreases and bellows 83' (Fig. 10) begins to collapse thus causing pin 'to move toward 'a in Fig.22. Lever 83' moves toward lla. Valve 66' moves from normal or equilibrium position 66' (shown in broken lines) toward the position 68a (shown in fulllines). Pressure fluid is then admitted to the right end (Fig. 7a) of cylinder 38', and rod 32 and coupling scoop hr move left to decrease the slippage of fluid-coupling H and to increase the speed of the supercharger D. .As rod 32 moves left, cam 2l0 turns clockwise toward 2l0y (Figs. 22, 23) to cause lever 83' to move away from 83a toward 83'11 so that the lever end moves away from 82's toward 83 and valve 65' moves left from 66a to 66' (Fig. 24) to close ports 69' and I. Then movement of rod 32' toward the left ceases. Cam 2) is so shaped that it places the valve 86 in the equilibrium position for closing ports 89' and I0 when a certain predetermined relation between impact pressure and position of coupling scoop hr has been satisfied. That relation will now be explained with reference to Fig. 28;

Curve I of Fig. 28 shows a typical example of the relation between coupling scoop position, ranging from 3.0" to 1.7" between center of coupling H to tip of coupling scoop hr, and impact pressure, ranging from value a or about 30" Hg absolute at ground level to value d or about 12.5" Hg at an elevation of about 21,000 feet. Curve I shows what the coupling scoop position should be for impact pressure values a to i at the coupling speed corresponding to slip curve III in order that the supercharger D will run at speeds providing, for example, approximately 9600 pounds per hour air flow. At ground level, represented by pressure a (about 30 Hg), the coupling scoop tip is 2.9" from coupling axis with a coupling slip value of about 56% according to curve III. This means that the supercharger D operates normal ly at ground level at such speed that it will not cause any restriction to air flow at the rate oi. 9600 pounds per hour as effected by supercharger F, and may even aid normally in maintaining such rate of air flow.

Curve II, for Normal part throttle slip,- shows the relation between impact pressure and coupling slip for normal or part throttle operation where the pressure selected to be maintained by the throttle controller TC is no greater than 25" Hg, such as required for cruising with minimum power.' Fig. 26 (bottom) shows the various positions of pin 2 (connecting the piston rod 32 with link 2l3, see Fig. 7a) which will effect the coupling slips called for by curve II. Positions II, 2l4a 2M7 on line 2l4l are the positions of pin 2l4 which have been found to give the C011". pling slip called for by curve II when the impact pressures are'from a to 9'. At the upper left of Fig. 26 are shown various equilibrium positions of lever 83' marked a to j. These equilibrium positions are those which cause the valve which controls the fluid coupling control servo to be in the position 66' (broken lines, Fig, 22) closing ports 69' and i0; and these equilibrium positions are determined by the location of fulcrum point 84' and by the location of cam 2l0.

10 The various locations of fulcrum 84" are determined by pressures a' to! in bellows 89'. The location of cam 2l0 is determined by various posi-' tions II, 2l4a to j of pin 2 and by the corresponding positions of pin 2i! (on end of lever M8) at Hm a to d or are Hm whose radius is lever 2l6, starting at 11m. and whose center is the axis of shaft 2 at position 11m. Reference II in Fig. 26 identifies parts 2, 2l5, 2", 2 with line II in Fig. 28 which is the coupling slip curve for pressure selections up to 25" Hg. At ground level, the slippage is 65%indicated by the left end of line H. Point 112144 is the starting point of pin 2l4a, point Hm is the starting point of pin 2i5, and Ham is the starting location of lever 2|. for ground level impact pressure a or 30" Hg. As altitude increases, altitude or impact pressure decreases from a to I. pin 2 moves from 11am to H214 on-line 2m, and pin 2"! moves on are 11m from a to 1 and cam 2"! turns clockwise to cause lever 83 to move to equilbrium positions a to 4. Thus for all pressure selections up to and including 25" Hg, there is a definite schedule of relations between altitude pressure and coupling slip as represented by line II in Fig. 28. This schedule is suitable for part load operation of the engine to meet the requirements of minimum cruise.

Under curve II of Fig. 28, there are curves III, IV and V of substantially the same slope as curve II but having starting points which are lower in coupling slip value. Curve III, for Military at 55" Hg, which is the curve for a pressure selection of 55", has a ground-level starting point of 56% coupling slip. Curve IV, for Emergency at 60" Hg, which is the curve for pressure selection of 60", has a ground level starting point of 51% coupling slip. Curve V, for Emergency at Hg, which is the curve for a pressure selection oi 65", has a ground level starting point of 46% coupling slip. -As the pressure selection increases above 25" Hg, the starting point of coupling slip decreases; and coupling slip decreases from starting point as altitude and impact pressures decrease. Thus far we have been concerned only with decrease of coupling slip as impact pressure decreases. We shall now describe how we obtain the lowering of the starting point of percentage of coupling slip as pressure selection increases.

' Referring-to-Fig. 18, the lower end of lever ll'I which operates pressure selectingcam I05 carries a roller 230 engaging a cam 23l provided by a slot in a lever 232 pivoted on a stud 233 attached to housing 2 of controller TC. Lever 232 is connected by stud 234 with a link 235 connected at its lower end by stud 229 with a lever 228 attached to the shaft 2i2 which eccentrically supports the shaft 2 of cam 2l0 (Fig. 20). A spring 22! attached to a lug 226 of housing 2' and to the lever 228, urges the lever counterclockwise, the link 235 upwardly and lever 232 upwardly, upward movement being limited by contact of the cam 23l with the roller 230. The cam 23l is so shaped as to permit no upward movement of lever 232 until pressures higher than 25" Hg are selected. Then the higher the pressure selection, the greater will be the upward movement of lever 230 and the counterclockwise movement of lever 228 under the action of spring 221.

Normally lever 228 is in the full line position shown in Fig. 20, which position it occupies when the pressure selected is from 0" to 25". When the selected pressure exceeds 25" the lever 230 begins to move up. If, for example, the selected pressure is 65", lever illis in position Illa (Fig.

ii 18) and lever 230 moves to 230a and lever 228 (Fig. 20) moves to 228a. The axis of shaft 2H moves 51.5 counterclockwise from 11211 marked 65% to V211 marked 46% (Fig. 27). This means that the ground level Starting point of coupling slip has decreased from 65% to 46%. In other words, we have dropped from curve II (Fig. 28) to curve V which represents slip values for impact pressure values when the pressure selection is 65". The starting point of pin 2 has been shifted left from An or to av (Fig. 27) or from 1121111 to V2145 on line 2 I 41 (Fig. 26). This happens because cam 2H1 moves from V2111 to V'Vzw (Figs. and 2'7) immediately following change of pressure selection from a low value 25". Therefore there must be a left movement of the coupling scoop h: before cam 2!!) is brought to position V210 (Fig. 25) when it locates lever 83' in the ground level equ librium position 83'a. The first position of stud 2I5. when cam center ,is at V211 (Fig. 27),

' is point a46 on are V215 marked 46%. The other positions corresponding to impact pressures b to 7' are marked M6 to 546 on arc V215.

If the selected pressure has been curve III (Fig. 28) would represent the relation between stud 2I5 is at an; on arc 111215 marked 56% and having its center at III211 which is 32 away from normal. Select on of 55" pressure had caused shaft 2I2 to move the axis of cam shaft 2| I to position I I211. The other positions of stud 2I5 for the 55" pressure selection are shown by points b to a on arc III215 and correspond to impact pressures b to 7'.

If the selected pressure had been 80", curve IV (Fig. 28) would represent the relation between coupling s ip and impact pressure. The starting point of pin 2 would be at IVma marked 51% (Fg. 2 or arv (F 2'?) to indic te a ground level cou ing s ip of 51%. The startin point of stud 2I5 is at (1 1 on are W215 marked 51% and having its center at IV211 which is 42.1" away from n rm l. Se ection of 60" pressure had caused s aft 2I2 to move the axis of cam sha t to position IV2 1. The ot er positions of stud 2 I 5 f r the 60" press e selection are shown by points b to 9 on are rvm and correspond to impact pressures b to If t e selected pressure had been curve V (Fi 28) would renre ent the relati n between cou l ng s ip and imp ct pre sure. The startng poi t 0* pin 2! would be at V2149, marked 46% (Fig. 26) 01' av (Fi 2'7) t indicate a ground leve coupling slip of 46%. The starting point of stud H5 is at (146 on arc V215 marked 46% and hav ng its cen er at V211 which is 515 away from normal. Se ect on of 65" pressure had caused shaft 2I2 to move the ax s of cam shaft to posi ion V211. The other positions of stud M5 for the 65" press re seection are shown by points 12 to 'i on are V215 and correspond to impact pressuresbto d.

From Fig. 27 it will be noted that the a" position of stud 2I5 for each of the cam shaft axis locations H211, H1211, W211, V211 causes the cam 2! to be in posit ons 11210, 111210, IV210 and V210 respect-vely. and that earn positions H2111, III210, W210, V210 all cause the lever 83' to be in ground level equilibrium position a. It is true that, for all locations of axis of cam shaft 2| I, when the stud 2I5 is in any of its 12 positions (either on are 11215 or III215 or W215 or V215) cam 2I8 will locate lever 83' at its b equilibrium position correspon ing to impact pressure b. The foregoing is true for'the other positions 0 to? of stud 2 I 5.

Curve VI of Fig. 28 chart shows the relation between movement of eccentric shaft 2I2 and starting point of coupling slip. Point ii on curve VI-is vertically below 0 on the eccentric scale and horizontally opposite 65% slip on curve II. Point iii on curve V1 is vertically below 32 on the eccentric scale and horizontally opposite 56% on curve III. Point in on curve VI is vertically below 415 on the eccentric scale and horizontally opposite 51% on curve IV. Point 12 on curve VI is vertically below 51.5 on the eccentric scale and horizontally opposite 46% on curve V. These values correspond with the slip percentages and eccentric angles found in Fig. 27.

Curve Xd of Fig. 30 shows that outside temper-ature decreases as altitude increases; and curve Xc shows that supercharger air temperature increases with altitude increase. Detonation point depends on fuel temperature and pressure. As temperature increases, the pressure must be lowered to avoid detonation. Curve III (Fig. 28) represents a coupling sli-p decrease which is correct for pressure selection of 55" Hg when impact chamber pressure increases from value a (about tion. For higher pressure selections like 60 and 65" this rate cannot be maintained throughout the same altitude range without causing detonation. We therefore allow approximately the rate indicated by curve III to be maintained up to certain altitude, and then cause a reduction in the rate of coupling slip decrease, so that detonation will be avoided. In Fig. 28 chart, line VII represents' the pick-up line. It intersects curve V at about the 16.7" impact pressure point and curve IV at about the 14.5" impact pressure point. This means that, When 65" pressure is selected, coupling slip follows curve V from 30" to 16.7" impact pressure and then follows the pick-up line VII to pressure 9' or 12.5"; and that, when 60" pressure is selected, coupling slip follows curve IV from 30" to 14.5" impact pressure and then follows .the pick-up line VII to pressure 9'. The pickup point on curve V (Fig. 28) is marked pick-up V on are V215 (Fig. 2'7) and the pick-up point on curve IV is marked pick-up IV on arc W215.

Pick-up is the term applied to the operation of lever 2 I6 (Fig. 20) in imparting a clockwise movement to lever 228 in subtracting some of the arcuate movement of cam shaft 2 which is obtained by virtue of a high pressure selection. For example, if the selected pressure was 65", the arcuate movement of the axis of cam shaft2l I was 515 to V211 in Fig. 27. By the time the 7 position of stud 2I5 is reached, the axis of the cam shaft 2! I should be at III211. To efiect this return movement while stud 2I5 carried by lever 2I6 is moving from a to pick-up V on are V215, the screw 2I8 on lever 2 moves from 2I82: (Fig. 20) to 2I8y where it contacts lever 228. As lever H8 is moved by stud 2I5 from the pick-up V position to the 7' position, lever 228 is moved by screw 2I8 through an angle such that the axis 2 of the lever 2I6 and the cam 2") moves back to 111211. This has the effect of a reduction in pressure selection between altitudes corresponding to impact pressure 16.7" and 12.5". Similarly, when the selected pressure was 60 requiring, initially, cam shaft position IVzn, pick-up IV on are IVm indicates where the screw 218 of lever 2|! picks up the lever 228 and causes cam shaft axis to shift from IVm to IIIan as the impact pressure changes from about 14.5" to 12.5" or value.

Figs. 24 and 25 show the various positions of cam 2H) where pressure selection effects the initial shift of cam position and operation of the scoop servo causes the final shift of cam position. The cam stands normally at H and the valve control lever at 83'. Pressure of 65" is selected and the cam moves orbitally around axis 2l2 to Wm (as in Fig. 27). The scoop moves toward coupling center to increase the slip starting point from 65% to 46% and cam moves to V210 (as in Fig. 27) to bring lever 83' back to the ground level equilibrium position a. As altitude increases and impact pressure decreases, bellows 8! contracts and pin 84 moves toward 84'a (Fig. 24), and lever 83 moves toward 83a to move valve 66 toward right from equilibrium position to cause the scoop servo to move further toward the coupling axis to decrease slip. At the pick-up point (pick-up V" on are V215, Fig. 27), cam H0 is located at 2l0a: and lever 83 is located at 83'x, while the valve 66 is still to the right of its equilibrium position. During the pick-up, cam 2l0 moves orbitally around the axis of shaft MI in a clockwise direction while rotating about its own axis and comes to position 2 I011 causing lever 83 to be located in equilibrium position 83'y which corresponds to the j position of lever 83 shown in Figs. 26 and 27.

The Fig. 29 chart shows the relation of coupling slip to obtainable pressure at various altitudes from sea level to 21,000 corresponding to impact pressure from a to 9'. The pick-up line VIIa of this chart shows for example that, during ascent from 15,000 to 21.000 with a 65'. pressure selection, the controller operates in eflect to reduce the selected slip to that required for 55" pressure selection in order to avoid detonation.

With reference to Fig. 30, we will show how the foregoing principles are applied to certain engines. Curve Xd represents standard atmospheric temperature for altitudes ranging from 0 to 21000 feet; curve XId represents standard atmospheric temperature minus 50 F. or winter condition; and curve XIId represents standard atmospheric temperature plus 50 F. or summer condition. Curve Xc represents the air or mixture temperature after being compressed by the superchargers (manifold mixture) corresponding to standard intake air Xd; similarly XL and XIIe represent the after-supercharger mixture or air temperature corresponding to intake air XL! and XIId respectively. Engine detonation occurs at lower manifold pressure as the temperature of the mixture fed to engine increases. Lines Xe, XI, XIIa, represent the maximum pressure beyond which detonation develops when manifold mixture temperatures are X42, X10, VIIc respectively, or temperatures of intake air to engine are Xe. XIa, XIIa. Lines X8, XIa, XIIa, are sometimes called border-line detonation manifold pressure curves" and represent the maximum manifold pressure at which a given engine and fuel can operate without detonation for given outside air temperatures and altitude. Lines Xa, XIs, XIIa show also that in order to obtain the maximum power from the engine, if there are no other mechanical limitations to its strength, maximum manifold pressure can be increased, for a given altitude, as outside air temperature is decreased. In other instances the above practice can be followed only up to a maximum pressure, sometimes below curve XIB, at which excessive overload may occur in the engine.

In the present description it has been assumed that the engine be capable of handling up'to 60" Hg manifold pressure. While summer conditions require keeping the manifold pressure below line XII; as air temperature decreases, the

pressure should be allowed to approach the 60" Hg without exceeding the detonation limit.

The results indicated in Fig. 30 have been approached by utilizing the fact that controller TC gives approximately a fixed schedule of blower speed versus impact (altitude) pressure independently of air temperature. If the engine throttle is wide open, the resulting manifold pressure boost (supercharger outlet pressure boost) is given by the following approximate equation:

at a given temperature T abs., the equation which is given by 60 being air density at To or zero degrees absolute temperature. From the above it, can be seen that a control capable of furnishing a fixed schedule of blower (or blowers) speed vs. altitude will supply higher pressures with cooler air and lower pressures with hotter air.

Curves Xi), XII), XIIb, represent blower(s) outlet pressures available for the corresponding air temperature Xe, XIa, XIId and mixture temperature Xe, XIc, XIIc. Since Xb, XIb, XIIb do not exceed appreciably or are less than the corresponding borderline detonations X8, XIa, XIIa then they can be used as means of controlling detonation. The excess of manifold pressure above a constant pressure at 49" Hg, for example, (line XIIa at 21,000 ft.) and line XIa represent the gain or advantage of this type of control over a fixed pressure control set for safe opera tion against detonation with year around setting. To obtain above gain, if engine has adequate mechanical strength, manifold pressure selection by controller TC should be in excess of XIa. If mechanical limitation of the engine requires limiting the maximum pressure to 60" Hg, for example, then in winter controller TC will limit the maximum pressure to 60" Hg by throttling, while in summer controller PC will keep the maximum pressure below 60" so as not to exceed the values represented by XIIb.

When the pressure selection is in the range between 25" and 55 Hg, the pressure obtained through the control of the auxiliary supercharger by the controller'FC is at least equal to the manifold pressure selected by throttle controller TC, when operating in the summer (standard temperature plus 50 F.). In winter (standard temperature minus 50 F.), the controller FC of the auxiliary supercharger selects a higher pressure than that called for by the throttle controller TC; therefore, constant pressure is maintained by throttling by means of controller TC. Maintenance of constant pressure is necessary to coordinate pressure selection with propeller R. P. M. selection as eflected by control of the propeller pitch governor (not shown).

nation ring 9| and housing 2.

When the pressure selection is 60" Hg, which is the maximum-allowable selection for a particular engine, the throtle controller TC causes the fluid coupling controller FC to give manifold pressures according to Xb for standard temperature conditions and according to XIIb for. summer conditions (standard plus 50 F.). Xb is below Xa (borderline detonation for standard temperature; and the major portion of XIIb is below XIIa (border line detonation for summer condition). That part of XIIb which is above XIIa is not above to such extent as to cause harmful detonation. Both Xb and XIIb are below the 60 Hg pressure selection. Therefore the throttle controller TC keeps the throttle valve wide open; while the coupling controller FC controls to give the pressure indicated by Xb or XIIb.

When 60" Hg pressure is selected during winter conditions, the controller FC so controls the auxiliary supercharger as to obtain manifold pressures according to XIb which are above 60" Hg. The throttle controller TC will partly close the throttle in order that the pressure will not exceed 60" although the controller F is set to obtain pressure in excess of 60".

By such coordination of the controllers TC and FC, we are able to obtain the maximum selected pressure during winter operating conditions and avoid harmful detonations at higher tempera- I tures.

With better fuel and higher engine mechanical strength it may be possible to operate without detonation up to 65" Hg manifold pressure. In that case coupling slips for various impact chamber pressure would be as indicated by line V of Fig. 28.

By injecting a mixture of water and alcohol into the fuel mixture in order to effect reduction of temperature by evaporation, the engine can operate at pressure around 80" Hg, without detoous impact chamber pressures would be as indicated by line XIII. Fig. 28, and that portion of the pick-up line VII leading from the lower end of line XIII and to the right thereof.

In order to provide for operation of the engine at the pressures indicated by lines XIII and VII of Fig. 28- certain changes in the throttle controller which has been described heretofore are necessary. These changes are shown in Figs. 31,

32 and 33. The pressure selecting cam I of Fig. 8 which provided for the selection of pressures no higher than about 62" Hg, is now capable of selecting pressures up to 80" Hg, for example, by virtue of the use of the bumper spring 304 in bellows 89 (Fig. 31). In order that parts of the controller shown in Fig. 8 may be used without change, it is necessary to add spring 304 which is inactive until after certain high pressure selections have been made such as 50". Spring 304 is located between the end wall 30f of a metal cap 300 and a self-locking nut 306 adjustable along a rod 305 fixed to bellows end plate 81. Cap 300 has a flange 302 confined between bellows end For pressure selections ranging from the lowest to around 50" Hg the nut 306 is out of engagement with the sprin 304. The nut 306 is located in the recess 95" corresponding to recess 95 of the controller shown in Fig. 8 and in communication with a pipe 99 (Fig. 33) which is connected with the engine induction pipe, for example at the scroll f (Fig. 1) of the supercharger F. Recess 95" is closed by a plug 95" which, on being removed, provides access to the nut 300 so that it may be adjusted in In that case the coupling slips for variorder to determine at what engine intake pressure the spring 304 begins to exercise a control.

Lines AB--CD of Fig. 34 (on same sheet with Fig. 2'7) shows the relation of manifold pres-- sures to positions of the main control lever I25 when the throttle controller is constructed as shown in Fig. 31. For pressure selections up to and including 50" the spring 304 is inactive; but, when the lever I25 is so moved that cam I05 selects pressures in excess of 50", the pressures which are obtained are designated by the line CD which is substantially steeper than the portion B-C of the pressure line. At point C representing 50" the nut 305 has engaged the spring 304; therefore, after the manifold pressure ex ceeds 50" Hg, the bellows 89 is under the control of the spring 304. Since spring 304 is relatively stiff, the pressure will increase rapidly as indicated by line CD when the lever I25 is moved passed the 50" pressure position. This makes it possible to go to the pressure position without increasing the range of movement of lever I25. Fig. 18 shows a dial plate I28 with pressure marks up to 65". Fig. 33 shows a dial plate I28 with pressure graduations up to 80". The graduations from 25" to 50 inclusive are the same as the corresponding markings on dial 128; but the graduations 50" to 80" of dial I28 are relatively close together.

As stated before, the controller shown in Fig. 8 was designed for controlling the pressure of an engine capable of handling about 62" Hg, manifold pressure. That same engine can operate at pressure around 80" without detonation when a water and alcohol mixture is being injected with the liquid fuel into the induction passage. In order to protect the engine against operating at such high pressures when the water-alcohol mixture becomes exhausted, the controller shown in Fig. 31 provides a safety device in the form of a rod 339 whose end 350 projects normally into the path of movement of the lever 83 such a distance that, when the cam I05 is located for selecting pressures above 62" Hg, the lever 83will be prevented from following the cam I05. When water injection is not used, the lever 83 cannot move to the left of the position which corresponds to the 62" Hg setting of the cam I05, although the cam I05 may be moved to a higher pressure selecting position. The rod 339 is controlled automatically by a fluid pressure means which will now be described. Instead of the back plate 0 shown in Fig. 8, we use a back plate 8" which is shaped to provide an annular recess 3i0 for receiving the edge of a diaphragm 3H confined between the back plate 8" and a housing 3I2 secured to the plate 8" by screws 3i3. A pipe SM is attached to the plate 8" for the purposes of making a connection between a fluid pressure source and a recess 3 l 5 in plate 8", and a passage 316 connecting recess 3l5 with a chamber 3|! in the housing 3|2. The diaphragm 3 is clamped between plates 3! and 3l9 which are confined between a shoulder 320 on a rod 322 and a nut 32l screw-threadedly engaging the rod 322. The rod 322 slides in a sleeve 323 supported by the plate 8"; and a spring 324 urges the diaphragm 

